Door Frame Compartment of Cast Titanium and Structural Fuselage Part

a technology of cast titanium and structural fuselage, which is applied in the direction of fuselages, sustainable transportation, transportation and packaging, etc., can solve the problems of high production and assembly costs of such cfp components, high production and assembly costs, and high cost of corresponding conventional aluminum components, etc., and achieves low production costs, low weight, and easy repair
US20090146008A1Inactive Publication Date: 2009-06-11AIRBUS OPERATIONS GMBH
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Patent Information

Authority / Receiving Office
US · United States
Patent Type
Applications(United States)
Current Assignee / Owner
AIRBUS OPERATIONS GMBH
Publication Date
2009-06-11
Estimated Expiration
Not applicable · inactive patent

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Abstract

A door frame component of cast titanium for a door opening in an outer skin of an aircraft or space vehicle is provided, the component including a contact surface for bearing against the outer skin, wherein the contact surface is formed to correspond to an inner contour of the outer skin in such a manner that the contact surface essentially fills the contour. From a further viewpoint the invention makes available a structural fuselage part for an aircraft or space vehicle which comprises an outer skin which has a carbon fiber reinforced plastic material together with a door frame component of the type described.
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Description

CROSS-REFERENCE TO RELATED APPLICATIONS

[0001] This application claims the benefit of U.S. Provisional Application No. 60 / 908,592, filed Mar. 28, 2007, the entire disclosure of which is herein incorporated by reference.FIELD OF THE INVENTION

[0002] This invention relates to a door frame component for an air or space vehicle, and a structural fuselage part with such a door frame component.BACKGROUND OF THE INVENTION

[0003] Although it can be used on any door openings in lightweight structures, this invention and the problems on which it is based are explained in relation to a passenger door in the fuselage shell of an aircraft.

[0004] Fuselage shells for aircraft are normally produced in so-called lightweight design from an outer skin which is reinforced on the inside by a two-dimensional structure of stringers running in the longitudinal direction of the aircraft and ribs running transversely to the longitudinal direction of the aircraft as stiffening elements.

[0005] In order to provide a do...

Claims

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